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File xflr5.changes of Package xflr5

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Wed Dec 26 08:15:10 UTC 2012 - dmitry_r@opensuse.org

- Update to version 6.09
  * see included ReleaseNotes.txt for details
- spec file cleanup
  
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Tue Jun 26 00:00:00 UTC 2012 - adeperrois@xflr5.com

- xflr5 v6.07
  * fixed type 2 batch polar analysis
  * fixed the issue with incorrect 3D-panel calculations
  * Corrected the incorrect aileron control derivatives
  * Corrected the bug in wing analysis with ground effect
  * Corrected the bug in type 4 analysis for wings and planes
  * Corrected the bug which modified the chord length as twist increases:
    impact results for wings with high dihedral
  * Cleaned, corrected, and improved the code for B-Splines
  * Removed the option for Min/Max type controls in Stabillity Polars
  * Added an option to edit Wing Polar paramaters
  * Fixed the crash bug when defining wings with more than 16 span sections
  * Corrected a bug leading to incorrect results in stability derivatives
    with active controls (CPanel::RotateBC())
  * Removed the Splined Points Foil option
  * Other minor corrections and enhancements
  * Code cleaning

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Fri Jan 06 00:00:00 UTC 2012 - adeperrois@xflr5.com

- xflr5 v6.06
  * Minor corrections and improvements

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Sun Jul 24 00:00:00 UTC 2011 - adeperrois@xflr5.com

- xflr5 v6.05 beta, July 15th, 2011
  * For Type 7 polars, listed the control value instead of the aoa in the top drop down box
  * Added a calculation form to determine Re.sqrt(Cl) for foil Type 2 polars
  * Added the Japanese translation to the repository - thanks to Koichi
  * Minor corrections and improvements

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Sun May 15 00:00:00 UTC 2011 - adeperrois@xflr5.com

- xflr5 v6.04 beta, May 14th, 2011
  * added a settings save at each project save
  * added and option to view forces on panels as coloured arrows
  * fixed the incorrect setting of AVL-type controls for flaps in T7 analysis
  * added the missing write operation in the project file of the control variable for wing operating points
  * modified the setting of boundary conditions in T7 analysis with activated controls - impact on balanced aoa
  * modified the wing construction process to allow for a gap in the middle of the wing
  * corrected the bug which caused the disapperance of the left stability toolbar when switching to 3D view
  * corrected the bug which prevented from changing the default number of panels in naca foil generation
  * continued the code cleaning process

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Sun Feb 13 00:00:00 UTC 2011 - adeperrois@xflr5.com

- XFLR5v6.03 beta rpm release
  * modified the geometry connection between panels with dihedral and twist - may slightly impact the results
  * corrected the calculations with sideslip
  * added multi-threading capability for foil batch analysis
  * added an option to display the position of point masses in 3d-view
  * in the export to AVL of point masses, corrected the missing addition of wing x & z position
  * modified the export format to AVL of with wing flaps
  * added an option to highlight the currently selected operating point, or the mode in root locs view
  * changed the interface for stability analysis
  * added a properties dialog box option for operating points
  * corrected various minor bugs
  * made several minor enhancements

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Sun Dec 19 00:00:00 UTC 2010 - adeperrois@xflr5.com

- XFLR5v6.02 beta rpm release
  * added an option to load a background image in the foil direct design module
  * corrected some errors in CoG and inertia automatic calculations, with impact on results
  * did some deep code cleaning
  * re-organized the panel analysis code to perform only one far field calculation per operating point
  * optimized the panel method for increased speed of execution
  * corrected the mesh edition for NURBS bodies
  * changed the export format for graphs
  * implemented the stability method for mixed panel/vlm method
  * implemented the stability method for full 3D panel method
  * corrected the bug which lead to incorrect results in 3D panel with Neumann B.C.
  * corrected the error in the jump in potential at the wing's trailing edage in full 3d panel method
  * set the estimation of inertia properties at the time of polar definition instead of evaluating at the time of analysis
  * fixed the bug which could cause a crash when dragging a point in splines design
  * corrected the asymetric transition location for symetric wings
  * corrected the source strength influence of thick panels on thin surfaces, with impact on results for planes with body
  * corrected the Cp 3D color display for VLM2 analysis
  * added the influence of pressure forces acting on the body to induced pitching moment coefficient
  * added calculation of neutral point position based on Cma/Cza ratio
  * corrected various minor bugs
  * made several minor enhancements

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Thu Oct 14 00:00:00 UTC 2010 - adeperrois@xflr5.com

- XFLR5v6.01 beta rpm release
  * Corrected the incorrect balance speed in 3D type 2 polars for planes
  * Corrected the final moment calculation in stability analysis
  * Corrected the incorrect lift calculation in stability analysis

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Sat Sep 19 00:00:00 UTC 2010 - adeperrois@xflr5.com

- XFLR5v6.00 beta rpm release

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Fri Apr 3  00:00:00 UTC 2010 - adeperrois@xflr5.com

- First rpm release

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File xflr5.changes of Package xflr5

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